212 results about "Engineering technician" patented technology

The invention provides a finite element prediction system for welding and solidifying a crack in virtual environment, which relates to the technical field of finite element prediction software for welding and solidifying a crack, and the complex simulation and the prediction processes of welding and solidifying a crack are simplified into the simple operation and settings of an interface. A preliminary processing subsystem comprises an interface operating module, an MSC.Marc interface document module, a subprogram.f file module and an invocation MSC.Marc software executing and computing module, and a post processing subsystem comprises a MSC.Marc software computed result processing module, a MatrixVB function module, a Matlab software module and a graphic display module; a solidified crack predicting subsystem comprises a resistivity curve loading module, a judgment module and a result output module. The application of the invention enables a common welding engineering technician to carry out the numerical simulation and prediction for welding and solidifying a crack; the computed result is processed, and the storage space of a result file is decreased; the result file is converted into a file format convenient for graphic display, and the computed results of a temperature field and a stress strain field are visually displayed in a graphic form.

The invention discloses a saturated self-adjusting controller for a time-varying delay uncertain system. The controller comprises three parts, namely a self-adjusting limiter, a conventional PID controller and an anti-integral saturator, wherein the conventional PID controller generates a control command uc(t) according to the offset of the controlled parameter y(t) and a target value r(t) thereof; the self-adjusting limiter calculates a steady-state gain K of a time-varying delay uncertain object under the corresponding working condition under the driving of a working condition variable s(t), dynamically generates a limiting value according to the K and r(t), timely limits the uc(t) and generates a final control function u(t); and the anti-integral saturator limits the integral function in the PID controller according to the offset of the uc(t) and u(t) in order to solve the possible integral saturation problem. By applying the invention, an engineering technician can conveniently apply effective control to a class of time-varying delay uncertain systems widely present in the process industry on an industrial control system (device) or in the mode of combining a hardware circuit with software programming so as to improve the safety and operating level of the production process.

The invention relates to a method, a server and a system for automatically generating an ONU (Optical Network Unit) network element topology. The method comprises the following steps of: customizing an ONU network element topology rule of an optical line terminal (OLT) network element by the server; obtaining ONU configuration data information from the OLT network element; and automatically generating the ONU network element topology of an appointed OLT network element based on the customized ONU network element topology rule and the ONU configuration data information. Based on the invention, ONU network element data of EPON (Ethernet Passive Optical Network) OLT network element can be flexibly, fast and automatically generated on a network management system, and the problem of easy error because engineering technicians manually establish ONU network element topology data is solved.

The invention discloses a method for designing a controller of a time-varying aircraft model with uncertainty, which is used for solving the technical problem that the existing robust control theory lacks design steps, so the flight controller is hard to design directly. The technical scheme is as follows: the time-varying system segmentation robust stability and solvability conditions are given, selection of desired closed-loop poles of linear time-varying system state feedback is directly utilized and a constraint condition inequality direct design feedback matrix is given according to the characteristic that all the real parts of all the desired closed-loop poles are negative, so that the engineering technicians in the research field directly design the flight controller for the time-varying aircraft model with uncertainty obtained through wind tunnel or flight tests, thus solving the technical problem that the current researches only give the robust stability inequality but can not directly design the flight controller.

The invention discloses a method for designing a controller of a multiple time lag aircraft model, which is used for solving the technical problem that the existing robust control theory lacks the design step, so the flight controller is hard to design directly. The technical scheme is as follows: the multiple lag system segmentation robust stability and solvability conditions are given, selection of desired closed-loop poles of linear system state feedback is directly utilized and a constraint condition inequality direct design feedback matrix is given according to the characteristic that all the real parts of all the desired closed-loop poles are negative, so that the engineering technicians in the research field directly design the flight controller for the aircraft model with multiple time lag uncertainty obtained through wind tunnel or flight tests, thus solving the technical problem that the current research results only give the robust stability inequality but can not directly design the flight controller.

The invention discloses a method for testing an electromagnetic interference propagation path of a motor drive system of a pure electric vehicle. The method comprises the steps of platform building, lead wire numbering, frequency spectrum testing, comparing and analyzing and the like. By the method, the main propagation path of the electromagnetic interface in the system can be detected, and the intensity and the frequency band range of the electromagnetic interference on each propagation path can also be detected so as to help the engineering technicians to analyze the electromagnetic interference on the system harness, and direct the technicians to perform good electromagnetic compatibility design and rectification on the motor drive system, thereby improving the electromagnetic compatibility of the overall vehicle. The method disclosed by the invention is simple and easy to operate and has strong universality.

The invention discloses a method for designing a controller of a multi-interval aircraft model, which is used for solving the technical problem that the existing robust control theory lacks design steps, so the flight controller is hard to design directly. The technical scheme is as follows: the multi-interval system robust stability and solvability conditions are given, selection of desired closed-loop poles of linear system state feedback is directly utilized and a constraint condition inequality direct design feedback matrix is given according to the characteristic that all the real parts of all the desired closed-loop poles are negative, so that the engineering technicians in the research field directly design the flight controller for the multi-interval aircraft system model obtained through wind tunnel or flight tests, thus solving the technical problem that the current researches only give the robust stability inequality but can not directly design the flight controller.

The invention discloses an aircraft time lag varying model approximation and controller designing method, and aims to solve the technical problem that the existing robust control theory is lack of the design steps and an aircraft controller cannot be directly designed. The technical scheme is as follows: the robust stability solvable condition of a time varying approximation system is given, a closed loop expecting pole fed back by a linear system state is directly utilized for selection, and a given conditional inequality is given to design a feedback matrix directly according to the characteristic that the real part of all closed loop expecting poles are negative numbers. By utilizing the method, the aircraft model containing time lag varying uncertainty are obtained by engineering technicians in the research field during wind tunnel or flight test, and an aircraft controller can be designed directly, so that the technical problem in the current research that only the robust stability inequality is given and the aircraft controller cannot be designed directly is solved.

The invention discloses a reliability degree predication method for composite material based on fatigue life distribution. According to the method, firstly, the fatigue life distribution of the composite material is depicted through Mittag-Leffler distribution, then in combination with a corrected Miner equivalent damage principle, accumulated damaged statistics distribution of the composite material is determined, and finally by the adoption of a Monte Carlo method, fatigue reliability degrees of the composite material under the different numbers of load circulation times are predicated. Parameters of the Mittag-Leffler distribution are less than parameters of a frequently-used three-parameter Weibull distribution, and the physical significance of the parameters is clear; the improved Miner equivalent damage principle considers influences on the sequence of loads exerted on the composite material and is simple in technical characteristic and convenient to use for engineering technicians. The reliability degree predication method can be used for predicating the fatigue reliability degrees of the composite material, is a reference for drawing up a repairing plan of composite material components and has important theoretical and engineering significance.

The invention discloses a method for detection of partial discharge of a switch cabinet in the field of power grids. The method for detection of partial discharge of the switch cabinet comprises the steps that initial locating of a partial discharge point is conducted, namely the general position of the partial discharge point of the switch cabinet is determined through two ultrahigh-frequency sensors; accurate locating of the partial discharge point is conducted, namely the accurate position of the partial discharge point of the switch cabinet is determined through multiple ultrasonic sensors; phasing of the partial discharge point is conducted, namely phasing is conducted on the partial discharge point of the switch cabinet through a high-frequency current sensor and a transient earth voltage sensor, and the type of partial discharge is determined. The method for detection of partial discharge of the switch cabinet has the advantages that the problem of interference exiting in the process of detection of partial discharge of the switch cabinet is effectively solved, the credibility of a detection result is improved, accurate locating and phasing of the discharge position are achieved, locating of the partial discharge point of the switch cabinet is accurate to the centimeter level, the type of partial discharge is determined, and engineering technicians can quite conveniently grasp the operation conditions of the switch cabinet.

The invention discloses a method for computing an optimal anchoring angle of a rock slope wedge, and belongs to the technical field of analyzing the stability of a rock slope and strengthening the rock slope. A security coefficient of the wedge-shaped slope serves as an objective function, the angle and the direction of anchoring force serve as optimization variables, constraint conditions such as the balance equation of the wedge, the yield condition of a structural surface and the boundary condition are combined, and the method which is used for computing the optimal anchoring angle of the wedge and can maximize the security coefficient is provided. The computing method can compute and obtain the optimal anchoring angle of the wedge accurately, easily and conveniently, has the advantages of being clear in concept, high in computing accuracy and the like, and brings convenience for engineering technicians to carry out optimal design for strengthening the wedge so as to achieve the purpose of being safe and economical.

The invention discloses an automatic recognition method of a transformer substation touring robot and the touring robot. Graphic image analysis results of an LED display screen and an indicator lamp panel are obtained according to shooting of the touring robot for the LED display screen and the indicator lamp panel, then, the steps of pretreatment, zoning, recognition and output are carried out, accordingly, the information of the LED display screen and the indicator lamp are displayed in a digital mode, and the touring robot can recognize the transformer substation state displayed on an instrument and then outputs the recognized result to engineering technicians. The process of manual image recognition is omitted, the dead zone and mistaken judgment possibly caused by manual operation are avoided, the touring efficiency is improved, the labor cost is saved, and touring stability and reliability are improved.

The invention discloses a real-time OEE (Overall Equipment Effectiveness) data information processing method and system for equipment operation of a production line. According to the method, real-time data information is collected for the production line, a recording system with equipment operation time and OEE real-time data information of the production line is established, and information of production factors such as production shifts, equipment and products is collected and saved in the real-time data information system in a real-time manner. The method has the characteristics that a record table with equipment operation time and OEE real-time data information of the production line is drawn through collecting the real-time data of a PLC (Programmable Logic Controller) in a basic automatic LEVEL 1 network of the production line, so that the engineering technicians can see the OEE index in a real-time and dynamic manner to comprehensively reflect various losses caused by relevant production, equipment and quality of the production line in the production field. In addition, people can have the competitive production field by improving the OEE.

The invention discloses a robust flight controller design method which is used for solving the technical problem that the existing robust control theory lacks design steps, so the flight controller is hard to design directly. The technical scheme is as follows: the system robust stability and solvability conditions are given, selection of desired closed-loop poles of linear system state feedback is directly utilized and a constraint condition inequality direct design feedback matrix is given according to the characteristic that all the real parts of all the desired closed-loop poles are negative, so that the engineering technicians in the research field directly design the flight controller for the aircraft model with uncertainty obtained through wind tunnel or flight tests, thus solving the technical problem that the current researches only give the robust stability inequality but can not directly design the flight controller.

The invention discloses a method for designing an aircraft controller with the nonlinearity, which is used for solving the technical problem that an existing robust control principle is lack of design steps, so that a flight controller is difficult to directly design. The invention adopts the technical scheme that a robust stable solvability condition of a system with an uncertain nonlinear term is given out; closed-loop expectation poles fed back by a state of a linear system are directly utilized to select; and according to the characteristic that real parts of all the closed-loop expectation poles are all negative numbers, a limiting condition inequality is given out to directly design a feedback matrix. Therefore, engineering technicians in the research field can directly design the flight controller for a flight model with the uncertain nonlinear term, which is obtained by a wind tunnel or flight test; and the technical problem that in the current research, only a robust stability inequality is given out so as not to directly design the flight controller is solved.

The invention discloses a high-proportion censored data reliability interval estimation method based on proportion grouping re-sampling. The method includes the steps that firstly, life test data are grouped into complete data and censored data; secondly, repeated sampling is conducted according to a specific proportion; thirdly, distribution parameters and reliability point estimations are obtained; fourthly, repeated re-sampling is conducted by the adoption of a Bootstrap method, and corresponding distribution parameters and reliability point estimations are calculated; fifthly, the obtained reliability point estimations are sequenced, and then the reliability interval estimation is obtained. The method avoids appearance of zero-failure data in the process of repeated re-sampling, and normal operation of the method is guaranteed; the method needs less theoretical knowledge, is easy and convenient to calculate, is easy to implement, facilitates use of engineering technicians and has good application value.

The invention discloses a method for optimizing general parameters of a control surface transmission mechanism. The method comprises the following steps that analytical expressions of the line rigidity, torsional rigidity, torsion frequency, the steering engine actuator travel original length ratio and the transmission ratio deviation of the control surface transmission mechanism are established; a parameterized ADAMS model of the control surface transmission mechanism is established; the ADAMS model, an input file including input variables, an output file including measurement values and a command file for driving an ADAMS are packaged; optimization goals and constraint conditions are determined; a ModelCenter optimizer and the ADAMS model are used for optimizing the designed distance between a variable rudder shaft and a steering engine support, the length of a rocker arm and the height of the steering engine support with the determined optimization goals and the constraint conditions, and optimized results are obtained. By means of the method, the quick optimization design of the general parameters of the control surface transmission mechanism is achieved, and engineering technicians can conveniently use the method.

The invention provides a method for making section boards in river model tests. The method comprises the steps as follows: drawing curve scripts; drawing the scripts by control points; marking the scripts by texts; running the scripts in an AutoCAD (Auto Computer Aided Design); drawing a plurality of the section boards and adjusting the positions; and making the section boards. According to the invention, the predetermined section shapes are recorded in a text form and drawn in a script form in the AutoCAD, so that the method can be very easily mastered by general engineering technicians without complex programming; the practical situations of general drawing printers and mould-making veneers are fully considered in the process of drawing the section boards, so that the method is stronger in practicality and lower in cost; and the method is simple in technical principle and easy to operate, saves a large amount of manpower and material resources, greatly improves the efficiency of making the section boards, avoids errors caused by manual drawing of section data, and is worthy of popularization and application in a large amount of the river model tests in the future.

The invention discloses a vehicle controller software updating method and device and a vehicle. The method includes the steps that the current attribute information of each controller of the vehicle to be updated is obtained; the current attribute information of each controller is compared with the target attribute information of a corresponding controller in a cloud platform to determine whetherthe controller meet the software updating condition; if yes, the controller software is updated, wherein attribute information of the controllers at least includes controller name information, hardware version information and software version information. Automatic recognition of the controllers and automatic differentiated software update in the vehicle are achieved, which is beneficial for assisting engineering technicians quickly locating the vehicle state, so that the software updating operation is convenient.

The invention discloses a highway pavement, tunnel distress diagnosis system based on computer image processing. The highway pavement, tunnel distress diagnosis system comprises a hardware part and a software part. The hardware part comprises coherent type laser pavement detection equipment, three-dimensional continuous type laser detection equipment, a main control computer unit, a data recording storage unit, an electrical unit, and an environment guarantee unit. The software part comprises a highway tunnel distress information database, a distress processing module, a distress diagnosis module, an expert diagnosis platform, a backstage operation system, and other modules. After various function and performance debugging, the software part is proved to be provided with a highway pavement, tunnel distress diagnosis-related image processing function, a distress diagnosis function, an expert on-line diagnosis function, and a function of proposing a maintenance scheme and a suggested scheme, and is capable of providing a data, information, process, result integration highway pavement, tunnel distress detection mechanism. Highway, tunnel structural safety and driving safety are guaranteed, tedious work of engineering technicians is reduced, and a significant meaning is provided for environmental protection, reduction of soil and water loss, and reduction of maintenance costs.

The invention relates to an outburst prediction and forecast device based on coal bed drilled hole gas parameter detection. The outburst prediction and forecast device comprises a collecting tube, the collecting tube is connected with one end of a hose, the other end of the hose is connected with an air inlet of an air chamber through a filtering device, and sensors are arranged inside the air chamber and connected with a processing circuit which is connected with a display screen. An air outlet of the air chamber is connected with an air outlet tube, an anti-explosion electromagnetic valve is arranged on the air outlet tube, and an exhaust hole is formed in the end of the air outlet tube. The coal bed drilled hole gas detection device can determine gas concentration, gas flow, gas temperature and gas pressure inside coal bed drilled holes at the same time, and the data are displayed in real time, continuously recorded and easy to inquire; an engineering technician under a coal mine can master the danger level of outburst at a determined place accurately in time, and technical supports can be provided for safe and economical exploitation of an outburst coal bed.

The invention belongs to the technical field of bridge structural engineering, and in particular relates to a damaged prestressed concrete flexural member decompression moment test method. A damaged prestressed concrete flexural member decompression moment test system adopted by the method comprises a bridge, a vertical load applying device, a surface strain gauge and a data acquisition instrument, wherein the vertical load applying device is arranged on a to-be-detected cracking section of the bridge; the surface strain gauge is installed on the surface of outer edge reinforcement without reinforcement cover concrete at a tensile area of the to-be-detected cracking section of the bridge; the data acquiring instrument is connected with the surface strain gauge through a conductor. Compared with the prior art, the damaged prestressed concrete flexural member decompression moment test method is simple to operate, accurate and reliable in result, easily mastered by engineering technicians, and is suitable for detecting and evaluating the cracked prestressed concrete flexural member decompression moment.

The invention discloses a supporting design specialist system for a bolt-grouting of a coal mine soft rock tunnel, belonging to the control of a coal mine tunnel pressure and wall rocks. The system comprises (1) a specialist knowledge module of bolt-grouting supporting in a soft rock tunnel; (2) a successful case database module of bolt-grouting supporting project practices in the soft rock tunnel; (3) a primitive data input module of a newly-established soft rock tunnel project; (4) a form inference design module of bolt-grouting supporting in the soft rock tunnel; (5) a parameter inference design module of bolt-grouting supporting in the soft rock tunnel; (6) a structural bearing capability evaluation module of bolt-grouting supporting in the soft rock tunnel; (7) a design report automatic generation module of bolt-grouting supporting in the soft rock tunnel; and (8) a constructional assignment graph drawing module of bolt-grouting supporting in the soft rock tunnel. According to the system, calculation and analysis processes on mathematics and mechanics involved in the bolt-grouting supporting design of the soft rock tunnel are embedded into a background of the system for processing, and according to a design result, a design report of bolt-grouting supporting is rapidly compiled, and a constructional assignment graph of bolt-grouting supporting is drawn. The system widely faces to the front engineering technician of a spot coal mine, and has strong practicability.

The invention discloses a method for constructing a dynamic relevant fault management system of an airborne network, and belongs to the technical field of electronic information. The method comprises the following steps: firstly, for a static physical structure of an airborne network system in a certain comprehensive test, constructing a product tree and a topological graph for a texted structure part; then, for a dynamic test process of the airborne network system in the comprehensive test, constructing a test item tree for the texted structure part; establishing a data model RI of the fault management system according to the product tree, the topological graph and the test item tree; then, for arbitrary two fault cases fi and fj in the data model RI, judging and determining the dynamic association information between the two fault cases fi and fj; and finally performing brightness display and storage on the topological graph. By adoption of the method disclosed by the invention, reference is provided for engineering technicians to intuitively discover weak links causing relevant faults easily and belonging business logic paths in the design and troubleshooting of avionics systems, and reference is also provided for purposeful reinforcement and improvement of the system.